Patents by Inventor Bhawan B. Patel
Bhawan B. Patel has filed for patents to protect the following inventions. This listing includes patent applications that are pending as well as patents that have already been granted by the United States Patent and Trademark Office (USPTO).
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Patent number: 10436114Abstract: A gas turbine engine has a combustor supported in a gas generator case. A baffle apparatus is attached to the gas generator case, surrounding an upstream section of the combustor to create at least one passage for directing an air flow discharged from a compressor diffuser to pass therethrough for cooling the combustor. The at least one passage extends from an upstream end of the combustor and has a passage exit immediately upstream of a dilution hole in the combustor. The baffle apparatus is configured to increase a velocity of the air flow entering the at least one passage and passing over the combustor.Type: GrantFiled: August 26, 2015Date of Patent: October 8, 2019Assignee: PRATT & WHITNEY CANADA CORP.Inventors: Bhawan B. Patel, Oleg Morenko
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Patent number: 10378775Abstract: A heat shield for a gas turbine engine having a combustor includes an annular configuration extending substantially 360 degrees about the combustor for protecting a dome portion thereof, which is formed by radially extending flanges of inner and outer liners of the combustor. The heat shield fixedly secures the radially extending flanges of the inner and outer liners together in a sealing relationship such as to structurally form the dome portion of the combustor. The heat shield is disposed internally within the combustor and substantially entirely overlying the dome portion. The heat shield includes at least two separate heat shield segments cooperating to provide the annular heat shield, each heat shield segment being sheet metal and including at least two circumferentially spaced apart openings therein for receiving fuel nozzles therethrough. Each of the heat shield segments has a circumferential span not exceeding 180 degrees.Type: GrantFiled: March 23, 2012Date of Patent: August 13, 2019Assignee: PRATT & WHITNEY CANADA CORP.Inventors: Bhawan B. Patel, Oleg Morenko
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Publication number: 20180328586Abstract: A fuel injector for a fuel spray nozzle of a gas turbine engine combustor includes an angular lip axially projecting into an upstream section of an annular passage to guide a fuel layer vortex to flow along a radially outer passage wall of the annular passage and to guide an air layer vortex to fill into and pass through an annular space between the fuel layer vortex and a radially-inner passage wall of the annular passage. The air layer vortex is free of mixing with the fuel layer vortex before the fuel layer vortex is discharged from the annular passage for fuel atomization.Type: ApplicationFiled: July 11, 2018Publication date: November 15, 2018Inventors: Bhawan B. PATEL, Oleg MORENKO
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Patent number: 10047959Abstract: A fuel injector for a fuel spray nozzle of a gas turbine engine combustor includes an angular lip axially projecting into an upstream section of an annular passage to guide a fuel layer vortex to flow along a radially outer passage wall of the annular passage and to guide an air layer vortex to fill into and pass through an annular space between the fuel layer vortex and a radially-inner passage wall of the annular passage. The air layer vortex is free of mixing with the fuel layer vortex before the fuel layer vortex is discharged from the annular passage for fuel atomization.Type: GrantFiled: December 29, 2015Date of Patent: August 14, 2018Assignee: PRATT & WHITNEY CANADA CORP.Inventors: Bhawan B. Patel, Oleg Marenko
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Patent number: 9874148Abstract: There is provided a method for improving the combustion efficiency of a combustor of a gas turbine engine powering an aircraft. The method comprises selectively using two distinct fuel injection units or a combination thereof for spraying fuel in a combustion chamber of the combustor of the gas turbine engine. A first one of the two distinct fuel injection units is selected and optimized for high power demands, whereas a second one of the two distinct fuel injection units is selected and optimized for low power level demands. In operation, the fuel flow ratio between the two distinct injection units is controlled as a function of the power level demand.Type: GrantFiled: January 31, 2014Date of Patent: January 23, 2018Assignee: PRATT & WHITNEY CANADA CORP.Inventors: Bhawan B. Patel, Oleg Morenko
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Patent number: 9829198Abstract: A gas turbine combustor floating collar for mounting an igniter or fuel nozzle to a combustor is provided with an outer periphery in a non-circular shape, for example having at least one section thereof formed with a flat surface, such as a square or triangular shape. The outer periphery of the floating collar is complementary to and completely surrounded by an inner periphery surface of a recess of a boss affixed on the combustor, thereby preventing substantial rotation of the floating collar with respect to the boss.Type: GrantFiled: August 12, 2013Date of Patent: November 28, 2017Assignee: PRATT & WHITNEY CANADA CORP.Inventors: Honza Stastny, Bhawan B. Patel, Ram Kulathu, Sudhakara Reddy Annem, Balakrishna Gaja, Bharath Mandya Nagaraj
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Publication number: 20170184307Abstract: A fuel injector for a fuel spray nozzle of a gas turbine engine combustor includes an angular lip axially projecting into an upstream section of an annular passage to guide a fuel layer vortex to flow along a radially outer passage wall of the annular passage and to guide an air layer vortex to fill into and pass through an annular space between the fuel layer vortex and a radially-inner passage wall of the annular passage. The air layer vortex is free of mixing with the fuel layer vortex before the fuel layer vortex is discharged from the annular passage for fuel atomization.Type: ApplicationFiled: December 29, 2015Publication date: June 29, 2017Inventors: Bhawan B. PATEL, Oleg MARENKO
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Patent number: 9683744Abstract: A gas turbine engine comprises a combustion system comprising a secondary annular combustor and a primary combustor in fluid communication with the secondary combustor, a secondary fuel injector associated with the secondary combustor, a primary fuel injector associated with the primary combustor, and a ECU controlling fuel delivery to the secondary and primary fuel injectors. The primary fuel injector delivers fuel to the primary combustor. The ECU allows fuel to be delivered to the secondary fuel injector in addition to the primary fuel injector only when a fuel amount higher is requested delivered by the primary fuel injector. A method of operating a gas turbine engine is also presented.Type: GrantFiled: February 28, 2014Date of Patent: June 20, 2017Assignee: PRATT & WHITNEY CANADA CORP.Inventors: Bhawan B. Patel, Oleg Morenko
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Patent number: 9599022Abstract: A modular fuel nozzle tip for a gas turbine engine includes a body defining one or more fuel conveying passages extending therethrough, an annular cap having a radially inner shoulder surface interfacing with the peripheral end surface of the body to define a plurality of air channels extending through the head portion of the modular fuel nozzle tip. At least two fasteners fasten the annular cap to the body.Type: GrantFiled: January 30, 2013Date of Patent: March 21, 2017Assignee: PRATT & WHITNEY CANADA CORP.Inventors: Honza Stastny, Bhawan B Patel, John Greer, Parthasarathy Sampath
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Publication number: 20170058775Abstract: A gas turbine engine has a combustor supported in a gas generator case. A baffle apparatus is attached to the gas generator case, surrounding an upstream section of the combustor to create at least one passage for directing an air flow discharged from a compressor diffuser to pass therethrough for cooling the combustor. The at least one passage extends from an upstream end of the combustor and has a passage exit immediately upstream of a dilution hole in the combustor. The baffle apparatus is configured to increase a velocity of the air flow entering the at least one passage and passing over the combustor.Type: ApplicationFiled: August 26, 2015Publication date: March 2, 2017Inventors: Bhawan B. PATEL, Oleg MORENKO
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Patent number: 9366187Abstract: A slinger combustor has an annular combustor shell defining a combustion chamber having a radially inner fuel inlet for receiving a spray of fuel centrifuged by a fuel slinger. The combustion chamber has a fuel atomization zone extending radially outwardly from the fuel inlet and merging into a radially outwardly flaring expansion zone leading to a combustion zone. A plurality of nozzle air inlets are defined in the fuel atomization zone of the combustor shell. The nozzle air inlets have a nozzle axis intersecting the stream of fuel and a tangential component in a direction of rotation of the fuel slinger. A plurality of dilution holes are defined in the combustor shell and have a dilution axis intersecting the combustion zone. The dilution axis of at least some of the dilution holes has a tangential component opposite to the direction of rotation of the fuel slinger.Type: GrantFiled: March 12, 2013Date of Patent: June 14, 2016Assignee: PRATT & WHITNEY CANADA CORP.Inventors: Bhawan B. Patel, Oleg Morenko
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Publication number: 20150247641Abstract: A gas turbine engine comprises a combustion system comprising a secondary annular combustor and a primary combustor in fluid communication with the secondary combustor, a secondary fuel injector associated with the secondary combustor, a primary fuel injector associated with the primary combustor, and a ECU controlling fuel delivery to the secondary and primary fuel injectors. The primary fuel injector delivers fuel to the primary combustor. The ECU allows fuel to be delivered to the secondary fuel injector in addition to the primary fuel injector only when a fuel amount higher is requested delivered by the primary fuel injector. A method of operating a gas turbine engine is also presented.Type: ApplicationFiled: February 28, 2014Publication date: September 3, 2015Applicant: Pratt & Whitney Canada Corp.Inventors: Bhawan B. PATEL, Oleg MORENKO
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Patent number: 8978383Abstract: A fuel manifold assembly for a gas turbine engine is described and includes an annular manifold body and an annular heat shield assembly mounted to and surrounding the manifold body. The heat shield assembly has an inner surface facing the manifold body and spaced apart therefrom by an inner air gap, which substantially surrounds the manifold body, defined therebetween. The heat shield assembly has an outer surface facing away from the manifold body and spaced apart from the inner surface by an outer air gap substantially surrounding the inner air gap. At least the outer air gap is formed by a double wall configuration of the heat shield assembly.Type: GrantFiled: March 26, 2012Date of Patent: March 17, 2015Assignee: Pratt & Whitney Canada Corp.Inventors: Bhawan B. Patel, Oleg Morenko
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Publication number: 20150040568Abstract: A gas turbine combustor floating collar for mounting an igniter or fuel nozzle to a combustor is provided with an outer periphery in a non-circular shape, for example having at least one section thereof formed with a flat surface, such as a square or triangular shape. The outer periphery of the floating collar is complementary to and completely surrounded by an inner periphery surface of a recess of a boss affixed on the combustor, thereby preventing substantial rotation of the floating collar with respect to the boss.Type: ApplicationFiled: August 12, 2013Publication date: February 12, 2015Applicant: PRATT & WHITNEY CANADA CORP.Inventors: Honza STASTNY, Bhawan B. PATEL, Ram KULATHU, Sudhakara Reddy ANNEM, Balakrishna GAJA, Bharath Mandya NAGARAJ
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Patent number: 8904800Abstract: A combustor dome heat shield and a louver are separately metal injection molded and then fused together to form a one-piece combustor heat shield.Type: GrantFiled: October 10, 2012Date of Patent: December 9, 2014Assignee: Pratt & Whitney Canada Corp.Inventors: Bhawan B. Patel, Lorin Markarian, Melissa Despres
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Publication number: 20140318145Abstract: There is provided a method for improving the combustion efficiency of a combustor of a gas turbine engine powering an aircraft. The method comprises selectively using two distinct fuel injection units or a combination thereof for spraying fuel in a combustion chamber of the combustor of the gas turbine engine. A first one of the two distinct fuel injection units is selected and optimized for high power demands, whereas a second one of the two distinct fuel injection units is selected and optimized for low power level demands. In operation, the fuel flow ratio between the two distinct injection units is controlled as a function of the power level demand.Type: ApplicationFiled: January 31, 2014Publication date: October 30, 2014Applicant: Pratt & Whitney Canada Corp.Inventors: Bhawan B. PATEL, Oleg MORENKO
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Patent number: 8794005Abstract: A reverse flow combustor for a gas turbine engine having an outer combustor liner and an inner combustor liner defining an annular combustion chamber, and a compound-angle frustoconical portion in the outer liner having a first and second conical slopes towards an engine centerline.Type: GrantFiled: December 21, 2006Date of Patent: August 5, 2014Assignee: Pratt & Whitney Canada Corp.Inventors: Nagaraja Rudrapatna, Oleg Morenko, Bhawan B. Patel
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Patent number: 8763401Abstract: There is provided an integrated fuel nozzle and ignition assembly for a gas turbine engine comprising a body having a fuel nozzle portion and an igniter portion. The fuel nozzle portion defines a fuel passage extending therethrough between a fuel inlet and a fuel outlet for directing a fuel flow into a combustion chamber. The igniter portion projects laterally from the fuel nozzle portion on a side thereof and comprises an igniter receiving cavity positioned adjacently and laterally on a side of the fuel passage. The assembly further comprises an igniter secured in the igniter receiving cavity for igniting the fuel flow discharged by the fuel passage.Type: GrantFiled: May 30, 2011Date of Patent: July 1, 2014Assignee: Pratt & Whitney Canada Corp.Inventors: Bhawan B. Patel, Enzo Macchia, Oleg Morenko, George Guglielmin
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Patent number: 8677731Abstract: A hybrid combustor combines two distinct fuel injection sources to spray fuel in the combustor. The combustor combines a rotary fuel slinger for spraying fuel in a first combustion zone during high power level and cruise conditions and a set of fuel nozzles for spraying fuel in a second combustion zone during lower power level and starting conditions.Type: GrantFiled: June 12, 2013Date of Patent: March 25, 2014Assignee: Pratt & Whitney Canada Corp.Inventors: Bhawan B. Patel, Oleg Morenko
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Publication number: 20130327054Abstract: A hybrid combustor combines two distinct fuel injection sources to spray fuel in the combustor. The combustor combines a rotary fuel slinger for spraying fuel in a first combustion zone during high power level and cruise conditions and a set of fuel nozzles for spraying fuel in a second combustion zone during lower power level and starting conditions.Type: ApplicationFiled: June 12, 2013Publication date: December 12, 2013Inventors: Bhawan B. PATEL, Oleg MORENKO